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Performance of an aerodynamic yaw controller mounted on the space shuttle orbiter body flap at Mach 10A wind-tunnel investigation of the effectiveness of an aerodynamic yaw controller mounted on the lower surface of a shuttle orbiter model body flap was conducted in the Langley 31-Inch Mach 10 Tunnel. The controller consisted of a 60 deg delta fin mounted perpendicular to the body flap lower surface and yawed 30 deg to the free stream direction. The control was tested at angles of attack from 20 deg to 40 deg at zero sideslip for a Reynolds number based on wing mean aerodynamic chord of 0.66 x 10(exp 6). The aerodynamic and control effectiveness characteristics are presented along with an analysis of the effectiveness of the controller in making a bank maneuver for Mach 18 flight conditions. The controller was effective in yaw and produced a favorable rolling moment. The analysis showed that the controller was as effective as the reaction control system in making the bank maneuver. These results warrant further studies of the aerodynamic/aerothermodynamic characteristics of the control concept for application to future transportation vehicles.
Document ID
19950017977
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Scallion, W. I. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-109179
NAS 1.15:109179
Accession Number
95N24397
Funding Number(s)
PROJECT: RTOP 242-80-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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